Airworthiness Directives; Air Tractor, Inc. Models AT-502, AT-502A, AT-502B, AT-602, AT-802, and AT-802A Airplanes, 66661-66663 [E6-19153]
Download as PDF
<![CDATA[
Federal Register / Vol. 71, No. 221 / Thursday, November 16, 2006 / Rules and Regulations
compliance with the actions in paragraph
(f)(2) of this AD.
No Reporting Required
(h) Although the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–27A0146 and Boeing Alert Service
Bulletin 757–27A0147, both dated October
14, 2004, describe procedures for submitting
a sheet recording accomplishment of the
service bulletin, this AD does not require that
action.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(j) You must use the service information in
Table 2 of this AD to perform the actions that
are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference of these documents in
66661
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Boeing Alert Service Bulletin
Revision level
757–27A0146 ..........................................................................................................................
757–27A0147 ..........................................................................................................................
757–57A0058 ..........................................................................................................................
Original .............................
Original .............................
1 .......................................
Issued in Renton, Washington, on October
31, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–19164 Filed 11–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25260; Directorate
Identifier 2006–CE–37–AD; Amendment 39–
14826; AD 2006–23–14]
RIN 2120–AA64
Airworthiness Directives; Air Tractor,
Inc. Models AT–502, AT–502A, AT–
502B, AT–602, AT–802, and AT–802A
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
rmajette on PROD1PC67 with RULES1
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Air Tractor, Inc. (Air Tractor) Models
AT–502, AT–502A, AT–502B, AT–602,
AT–802, and AT–802A airplanes. This
AD requires you to repetitively visually
inspect the rudder and vertical fin hinge
attaching structure (vertical fin skins,
spars, hinges, and brackets) for loose
fasteners, cracks, and/or corrosion. This
AD also requires you to replace any
damaged parts found as a result of the
inspection and install an external
doubler at the upper rudder hinge. This
AD results from two reports of in-flight
rudder separation from the vertical fin
VerDate Aug<31>2005
15:50 Nov 15, 2006
Jkt 211001
at the upper attach hinge area, and other
reports of airplanes with loose hinges,
skin cracks, or signs of repairs to the
affected area. We are issuing this AD to
detect and correct loose fasteners; any
cracks in the rudder or vertical fin skins,
spars, hinges or brackets; and/or
corrosion of the rudder and vertical fin
hinge attaching structure. Hinge failure
adversely affects ability to control yaw
and has led to the rudder folding over
in flight. This condition could allow the
rudder to contact the elevator and affect
ability to control pitch with consequent
loss of control.
This AD becomes effective on
December 21, 2006.
As of December 21, 2006, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
DATES:
To get the service
information identified in this AD,
contact Air Tractor, Inc., P.O. Box 485,
Olney, Texas 76374; telephone: (940)
564–5616; fax: (940) 564–5612.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590 or
on the Internet at https://dms.dot.gov.
The docket number is FAA–2006–
25260; Directorate Identifier 2006–CE–
37–AD.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Andrew McAnaul, Aerospace Engineer,
ASW–150 (c/o MIDO–43), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308–
3365; fax: (210) 308–3370.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
Date
October 14, 2004.
October 14, 2004.
January 10, 2002.
Discussion
On August 3, 2006, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Air Tractor Models AT–502,
AT–502A, AT–502B, AT–602, AT–802,
and AT–802A airplanes. This proposal
was published in the Federal Register
as a notice of proposed rulemaking
(NPRM) on August 3, 2006 (71 FR
45451). The NPRM proposed to require
you to repetitively visually inspect the
rudder and vertical fin hinge attaching
structure for loose fasteners, any cracks
in the rudder or vertical fin skins, spars,
hinges or brackets, or corrosion. The AD
would also require you to replace any
damaged parts found as a result of the
inspection and install an external
doubler at the upper rudder hinge.
Installation of the external doubler at
the upper rudder hinge is terminating
action for the repetitive inspection
requirements.
Comments
We provided the public the
opportunity to participate in developing
this AD. The following presents the
comments received on the proposal and
FAA’s response to each comment:
Comment Issue No. 1: Availability of
Manufacturer Service Information for
the Proposed AD
Jack Buster with the Modification and
Replacement Parts Association
(MARPA) provides comments on the AD
process pertaining to how the FAA
addresses publishing manufacturer
service information as part of a
proposed AD action. Mr. Buster states
that the proposed rule attempts to
E:\FR\FM\16NOR1.SGM
16NOR1
66662
Federal Register / Vol. 71, No. 221 / Thursday, November 16, 2006 / Rules and Regulations
require compliance with a public law by
reference to a private writing (as
referenced in paragraph (e) of the
proposed AD). Mr. Buster would like
the FAA to incorporate by reference
(IBR) Snow Engineering Co. Service
Letter #247, dated August 14, 2005,
revised May 17, 2006; and Snow
Engineering Co. Process Specification
Number 145, dated December 6, 1991.
We agree with Mr. Buster. However,
we do not IBR any document in a
proposed AD action, instead we IBR the
document in the final rule. Since we are
issuing the proposal as a final rule AD
action, the previously-referenced Snow
Engineering Co. documents are
incorporated by reference.
Comment Issue No. 2: Availability of
Manufacturer Service Information in the
Federal Register or the Docket
Management System (DMS)
Mr. Buster also requests IBR
documents be made available to the
public by publication in the Federal
Register or in the DMS.
We are currently reviewing issues
surrounding the posting of service
bulletins in the Department of
Transportation’s DMS as part of the AD
docket. Once we have thoroughly
examined all aspects of this issue and
have made a final determination, we
will consider whether our current
practice needs to be revised.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 945
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Total cost per
airplane
Labor cost
Parts cost
1 work-hour × $80 per hour = $80 ............................................................
$80
$75,600
Not Applicable .................................
Any required ‘‘upon-condition’’
repairs will vary depending upon the
damage found, and any replacements
required will vary based on the results
of the inspection. Based on this, we
have no way of determining the
potential repair and/or replacement
costs for each airplane or the number of
airplanes that will need the repairs and/
Labor cost
or replacements based on the result of
the inspections.
We estimate the following costs to do
the installation of the external doubler
at the upper rudder hinge:
Parts cost
5 work-hours × $80 per hour = $400 ..........................................................................................
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106 describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this AD.
rmajette on PROD1PC67 with RULES1
Total cost on
U.S. Operators
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
VerDate Aug<31>2005
15:50 Nov 15, 2006
Jkt 211001
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2006–25260;
Directorate Identifier 2006–CE–37–AD’’
in your request.
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
Total cost per
airplane
Total cost on
U.S. operators
$617
$583,065
$217
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
I 2. FAA amends § 39.13 by adding a
new AD to read as follows:
2006–23–14 Air Tractor, Inc.: Amendment
39–14826; Docket No. FAA–2006–25260;
Directorate Identifier 2006–CE–37–AD.
Effective Date
(a) This AD becomes effective on December
21, 2006.
E:\FR\FM\16NOR1.SGM
16NOR1
Federal Register / Vol. 71, No. 221 / Thursday, November 16, 2006 / Rules and Regulations
Affected ADs
Applicability
(c) This AD affects the following airplane
models and serial numbers that are
certificated in any category:
(b) None.
Model
(1)
(2)
(3)
(4)
66663
Serial Nos.
AT–502 and AT–502B ........................................................................
AT–502A .............................................................................................
AT–602 ................................................................................................
AT–802 and AT–802A ........................................................................
Unsafe Condition
(d) This AD results from two reports (one
Model AT–602 airplane and one Model AT–
802A airplane) of in-flight rudder separations
at the upper attach hinge area and other
reports of Models AT–502B, AT–602, and
AT–802/802A airplanes with loose hinges,
502/502B–0003 through 502/502B–2600.
502A–0003 through 502A–2582.
602–0337 through 602–1138.
802/802A–0001 through 802/802A–0215.
skin cracks, or signs of repairs to the affected
area. We are issuing this AD to detect and
correct loose fasteners; any cracks in the
rudder or vertical fin skins, spars, hinges or
brackets; and/or corrosion of the rudder and
vertical fin hinge attaching structure. Hinge
failure adversely affects ability to control yaw
and has led to the rudder folding over in
flight. This condition could allow the rudder
to contact the elevator and affect ability to
control pitch with consequent loss of control.
Compliance
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect visually the rudder and vertical
hinge attachment for loose fasteners; and inspect the rudder or vertical fin skins, spars,
hinges or brackets for cracks and/or corrosion.
Initially inspect upon reaching 3,500 hours
time-in-service (TIS), or within the next 100
hours TIS after December 21, 2006 (the effective date of this AD), whichever occurs
later, unless already done. Thereafter, repetitively inspect every 100 hours TIS. Installation of the external doubler at the
upper rudder hinge required by paragraph
(e)(2)(ii) or (e)(3) of this AD is terminating
action for the repetitive inspections required
by this AD.
Before further flight after any inspection required by paragraph (e)(1) of this AD where
you find any damaged parts. The installation of the external doubler at the upper
rudder hinge required by paragraph
(e)(2)(ii) or (e)(3) of this AD is the terminating action for the repetitive inspections
required by this AD.
Upon accumulating 5,000 hours TIS or within
the next 100 hours TIS after the effective
date of this AD, whichever occurs later, unless already done. The installation of the
external doubler at the upper rudder hinge
required by paragraph (e)(2)(ii) or (e)(3) of
this AD is the terminating action for the repetitive inspections required by this AD.
As of December 21, 2006 (the effective date
of this AD).
Follow Snow Engineering Co. Service Letter
#247, dated August 14, 2005, revised May
17, 2006.
(2) If you find any damage as a result of any inspection required by paragraph (e)(1) of this
AD, you must:
(i) Replace any damaged parts with new
parts; and
(ii) Do the installation of the external doubler at the upper rudder hinge.
(3) Do the installation of the external doubler at
the upper rudder hinge.
(4) Do not install any rudder without the external doubler at the upper rudder hinge required by paragraph (e)(3) of this AD.
Alternative Methods of Compliance
(AMOCs)
rmajette on PROD1PC67 with RULES1
(f) The Manager, Fort Worth Aircraft
Certification Office, FAA, ATTN: Andrew
McAnaul, Aerospace Engineer, ASW–150
(c/o MIDO–43), 10100 Reunion Place, Suite
650, San Antonio, Texas 78216; telephone:
(210) 308–3365; fax: (210) 308–3370, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
Material Incorporated by Reference
(g) You must use Snow Engineering Co.
Service Letter #247, dated August 14, 2005,
revised May 17, 2006; and Snow Engineering
Co. Process Specification Number 145, dated
VerDate Aug<31>2005
15:50 Nov 15, 2006
Jkt 211001
December 6, 1991, to do the actions required
by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Air Tractor, Inc., P.O. Box
485, Olney, Texas 76374; telephone: (940)
564–5616; fax: (940) 564–5612.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
Follow Snow Engineering Co. Service Letter
#247, dated August 14, 2005, revised May
17, 2006, and Snow Engineering Co. Process Specification Number 145, dated December 6, 1991.
Follow Snow Engineering Co. Service Letter
#247, dated August 14, 2005, revised May
17, 2006, and Snow Engineering Co. Process Specification Number 145, dated December 6, 1991.
Not Applicable.
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_ regulations/
ibr_locations.html.
Issued in Kansas City, Missouri, on
November 3, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–19153 Filed 11–15–06; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\16NOR1.SGM
16NOR1
]]>Agencies
[Federal Register Volume 71, Number 221 (Thursday, November 16, 2006)]
[Rules and Regulations]
[Pages 66661-66663]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19153]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25260; Directorate Identifier 2006-CE-37-AD;
Amendment 39-14826; AD 2006-23-14]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc. Models AT-502, AT-
502A, AT-502B, AT-602, AT-802, and AT-802A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Air Tractor, Inc. (Air Tractor) Models AT-502, AT-502A, AT-502B, AT-
602, AT-802, and AT-802A airplanes. This AD requires you to
repetitively visually inspect the rudder and vertical fin hinge
attaching structure (vertical fin skins, spars, hinges, and brackets)
for loose fasteners, cracks, and/or corrosion. This AD also requires
you to replace any damaged parts found as a result of the inspection
and install an external doubler at the upper rudder hinge. This AD
results from two reports of in-flight rudder separation from the
vertical fin at the upper attach hinge area, and other reports of
airplanes with loose hinges, skin cracks, or signs of repairs to the
affected area. We are issuing this AD to detect and correct loose
fasteners; any cracks in the rudder or vertical fin skins, spars,
hinges or brackets; and/or corrosion of the rudder and vertical fin
hinge attaching structure. Hinge failure adversely affects ability to
control yaw and has led to the rudder folding over in flight. This
condition could allow the rudder to contact the elevator and affect
ability to control pitch with consequent loss of control.
DATES: This AD becomes effective on December 21, 2006.
As of December 21, 2006, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone:
(940) 564-5616; fax: (940) 564-5612.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2006-25260; Directorate
Identifier 2006-CE-37-AD.
FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Discussion
On August 3, 2006, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Air Tractor Models AT-502, AT-502A, AT-502B, AT-
602, AT-802, and AT-802A airplanes. This proposal was published in the
Federal Register as a notice of proposed rulemaking (NPRM) on August 3,
2006 (71 FR 45451). The NPRM proposed to require you to repetitively
visually inspect the rudder and vertical fin hinge attaching structure
for loose fasteners, any cracks in the rudder or vertical fin skins,
spars, hinges or brackets, or corrosion. The AD would also require you
to replace any damaged parts found as a result of the inspection and
install an external doubler at the upper rudder hinge. Installation of
the external doubler at the upper rudder hinge is terminating action
for the repetitive inspection requirements.
Comments
We provided the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and FAA's response to each comment:
Comment Issue No. 1: Availability of Manufacturer Service Information
for the Proposed AD
Jack Buster with the Modification and Replacement Parts Association
(MARPA) provides comments on the AD process pertaining to how the FAA
addresses publishing manufacturer service information as part of a
proposed AD action. Mr. Buster states that the proposed rule attempts
to
[[Page 66662]]
require compliance with a public law by reference to a private writing
(as referenced in paragraph (e) of the proposed AD). Mr. Buster would
like the FAA to incorporate by reference (IBR) Snow Engineering Co.
Service Letter 247, dated August 14, 2005, revised May 17,
2006; and Snow Engineering Co. Process Specification Number 145, dated
December 6, 1991.
We agree with Mr. Buster. However, we do not IBR any document in a
proposed AD action, instead we IBR the document in the final rule.
Since we are issuing the proposal as a final rule AD action, the
previously-referenced Snow Engineering Co. documents are incorporated
by reference.
Comment Issue No. 2: Availability of Manufacturer Service Information
in the Federal Register or the Docket Management System (DMS)
Mr. Buster also requests IBR documents be made available to the
public by publication in the Federal Register or in the DMS.
We are currently reviewing issues surrounding the posting of
service bulletins in the Department of Transportation's DMS as part of
the AD docket. Once we have thoroughly examined all aspects of this
issue and have made a final determination, we will consider whether our
current practice needs to be revised.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 945 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. Operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80.............. Not Applicable.................. $80 $75,600
----------------------------------------------------------------------------------------------------------------
Any required ``upon-condition'' repairs will vary depending upon
the damage found, and any replacements required will vary based on the
results of the inspection. Based on this, we have no way of determining
the potential repair and/or replacement costs for each airplane or the
number of airplanes that will need the repairs and/or replacements
based on the result of the inspections.
We estimate the following costs to do the installation of the
external doubler at the upper rudder hinge:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
5 work-hours x $80 per hour = $400.............................. $217 $617 $583,065
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106 describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2006-25260; Directorate Identifier 2006-CE-37-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2006-23-14 Air Tractor, Inc.: Amendment 39-14826; Docket No. FAA-
2006-25260; Directorate Identifier 2006-CE-37-AD.
Effective Date
(a) This AD becomes effective on December 21, 2006.
[[Page 66663]]
Affected ADs
(b) None.
Applicability
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
(1) AT-502 and AT-502B................. 502/502B-0003 through 502/502B-
2600.
(2) AT-502A............................ 502A-0003 through 502A-2582.
(3) AT-602............................. 602-0337 through 602-1138.
(4) AT-802 and AT-802A................. 802/802A-0001 through 802/802A-
0215.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from two reports (one Model AT-602 airplane
and one Model AT-802A airplane) of in-flight rudder separations at
the upper attach hinge area and other reports of Models AT-502B, AT-
602, and AT-802/802A airplanes with loose hinges, skin cracks, or
signs of repairs to the affected area. We are issuing this AD to
detect and correct loose fasteners; any cracks in the rudder or
vertical fin skins, spars, hinges or brackets; and/or corrosion of
the rudder and vertical fin hinge attaching structure. Hinge failure
adversely affects ability to control yaw and has led to the rudder
folding over in flight. This condition could allow the rudder to
contact the elevator and affect ability to control pitch with
consequent loss of control.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect visually the Initially inspect Follow Snow
rudder and vertical hinge upon reaching 3,500 Engineering Co.
attachment for loose hours time-in- Service Letter
fasteners; and inspect the service (TIS), or 247, dated
rudder or vertical fin within the next 100 August 14, 2005,
skins, spars, hinges or hours TIS after revised May 17,
brackets for cracks and/or December 21, 2006 2006.
corrosion. (the effective date
of this AD),
whichever occurs
later, unless
already done.
Thereafter,
repetitively
inspect every 100
hours TIS.
Installation of the
external doubler at
the upper rudder
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
is terminating
action for the
repetitive
inspections
required by this AD.
(2) If you find any damage Before further Follow Snow
as a result of any flight after any Engineering Co.
inspection required by inspection required Service Letter
paragraph (e)(1) of this by paragraph (e)(1) 247, dated
AD, you must: of this AD where August 14, 2005,
(i) Replace any damaged you find any revised May 17,
parts with new parts; and damaged parts. The 2006, and Snow
(ii) Do the installation of installation of the Engineering Co.
the external doubler at the external doubler at Process
upper rudder hinge. the upper rudder Specification
hinge required by Number 145, dated
paragraph December 6, 1991.
(e)(2)(ii) or
(e)(3) of this AD
is the terminating
action for the
repetitive
inspections
required by this AD.
(3) Do the installation of Upon accumulating Follow Snow
the external doubler at the 5,000 hours TIS or Engineering Co.
upper rudder hinge. within the next 100 Service Letter
hours TIS after the 247, dated
effective date of August 14, 2005,
this AD, whichever revised May 17,
occurs later, 2006, and Snow
unless already Engineering Co.
done. The Process
installation of the Specification
external doubler at Number 145, dated
the upper rudder December 6, 1991.
hinge required by
paragraph
(e)(2)(ii) or
(e)(3) of this AD
is the terminating
action for the
repetitive
inspections
required by this AD.
(4) Do not install any As of December 21, Not Applicable.
rudder without the external 2006 (the effective
doubler at the upper rudder date of this AD).
hinge required by paragraph
(e)(3) of this AD.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Fort Worth Aircraft Certification Office, FAA,
ATTN: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43),
10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone:
(210) 308-3365; fax: (210) 308-3370, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19.
Material Incorporated by Reference
(g) You must use Snow Engineering Co. Service Letter
247, dated August 14, 2005, revised May 17, 2006; and Snow
Engineering Co. Process Specification Number 145, dated December 6,
1991, to do the actions required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940)
564-5616; fax: (940) 564-5612.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on November 3, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19153 Filed 11-15-06; 8:45 am]
BILLING CODE 4910-13-P
